• 한국소음진동공학회:학술대회논문집
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• 한국소음진동공학회 2005년도 추계학술대회논문집
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• pp.852-855
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• 2005

Structural Dynamic Modification(SDM) is a technique to improve structure's dynamic characteristics by adding and removing substructures or changing material properties and shape of structures. This paper describes SDM techniques applied to a large structure with too many DOFs. The goal of this SDM technique is to modify a targe structure efficiently for its natural frequencies to avoid excitation frequencies. In this case, models reduced by Component Mode Synthesis(CMS) method that is a coupling technique are used to analyze a large structure efficiently. This paper considers a helicopter deck model with 55,000 DOFs as an application.

• 한국항공우주학회지
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• 제40권3호
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• pp.201-208
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• 2012

본 논문에서는 정지비행 조건에서의 무향실 내 축소 로터 실험을 이용해 Lowson의 하중 소음식과 FW-H의 음향상사식으로 예측한 이산 주파수 소음(Discrete frequency noise)을 검증하였다. 소음 예측 기법의 방향성(Directivity) 검증은 전반적으로 실험결과와 유사하게 예측되었으며, 거리에 대한 검증의 경우 근거리(Near-field)에서는 FW-H식의 예측결과가, 원거리(Far-field)에서는 Lowson식의 예측결과가 실험결과와 더 유사한 것을 확인하였다. 피치 각(Collective pitch angle)에 대한 검증의 경우 낮은 피치각에서는 FW-H식의 예측결과가, 높은 피치각에서는 Lowson식의 예측결과가 실험결과와 더 유사한 것을 확인하였다.

• Journal of the Korean Academy of Child and Adolescent Psychiatry
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• 제18권2호
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• pp.145-153
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• 2007

Objectives: This study was focused on the influence of chronic aircraft noise exposure on children's continuous performance, intelligence and reading skill. Methods: We enrolled 586 children in 4-6th grade of 7 primary schools near air base in Korea. Continuous performance was measured using the computerized ADS program. We analyzed 477-512 children on the visual continuous performance test, auditory continuous performance test, intelligence test, and reading and the vocabulary test. Intelligence was measured using vocabulary, digit span, block design, and digit symbol tests of K-WISC-III. Results: The commission error and variability deviation of auditory continuous performance test and reading test were significantly higher among children in schools with the helicopter noise and the fighting plane noise compared to children in the low noised schools. Conclusion: There was a possibility that chronic aircraft noise exposure was associated with impairment of the school performance. The result of our study also shows chronic aircraft noise was associated with reading ability.

• 한국광학회지
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• 제18권2호
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• pp.135-141
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• 2007

완전한 2차원 배열을 갖는 중적외선 대역의 $320\times240$ 검출기를 사용하는 3세대 열상 장비의 설계 및 제작은 이차원 배열 검출기 제작 기술의 발달과 영상 신호처리 기술의 진전으로 인해 최근 더욱 더 활발히 이루어지고 있다. 본 논문은 다양한 응용 분야에서 적외선 센서로 사용될 수 있도록 하기 위하여 소형 경량화 제작을 목표로 한 3세대 열상장비의 이중 배율 적외선 카메라의 설계와 Defocus용 셔터 렌즈에 의한 영상기반 불균일 보정 방식에 대해 다룬다.

• 지구물리와물리탐사
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• 제13권1호
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• pp.51-60
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• 2010

남극 킹조지섬 포케이드 빙하의 저면 지형과 내부 모습을 규명하기 위해서 2006년 11월에 4개 조사측선을 따라 헬리콥터 및 지상 레이다(GPR) 탐사를 실시하였다. 혼합위상인 단채널 지상 GPR 자료에 적용한 신호 역대합, f-k 구조보정 속도분석, 유한차분 깊이구조보정 등의 처리과정을 통하여 수직 분해능 향상, 속도함수 추출, 선명한 깊이영상 작성 등을 효과적으로 수행하였다. 헬리콥터 GPR 자료의 경우, 구조보정속도는 공기와 얼음의 2층모델을 가정한 평균제곱근속도로 구하였다. GPR 단연은 울퉁불퉁한 빙저면, 빙하 내부의 미끄러짐면, 운집된 산란잡음 등의 특징적 모습을 보여준다. 기반암까지의 최대 깊이는 포케이드 빙하와 목지들로우스키 빙하 사이의 경계능선 남동사면에 인접한 빙하 골짜기에서 79 m가 넘는다. 빙하 기저수 위에 복잡한 형태의 굴과 수 m의 폭을 갖는 독립된 빈 공간들의 존재를 지상 GPR 자료로부터 해석하였다. 빙하 중단 부근의 GPR 영상은 포토소만의 빙산 형성기작과 관련된 미끄러짐면, 단열, 단층 등의 구조를 보여준다.

• 한국소음진동공학회:학술대회논문집
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• 한국소음진동공학회 2005년도 춘계학술대회논문집
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• pp.132-137
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• 2005

This paper addresses what amount of whole-body vibration is exposed to pilots of UH60 helicopters during flight. To measure the whole-body exposed from the feet and seat, the 12-axis vibration measurement system was used. It enables simultaneous measurement of vibration exposure from the body contact area of the feet, hip and back. The measured 12-axis vibration signals are exploited to the comfort level of UH60 helicopters during flight. It is shown that the evaluated ride value is close to $0.74{\sim}0.79m/s^2$ and that it is equivalent to the semantic scale of 'fairly uncomfortable'. To assess the health effects of whole-body vibration exposed to pilots of UH60 helicopters during their flight, the rms-based and VDV(vibration dose value)-based evaluation results of measured four-axis vibration signals are shown in this work. The fatigue-decreased proficiency limit, whose level is half of the exposure limit, is expected to come after the two-hour flight. The exposure limit is shown to reach after the 10-hour flight.

• 한국소음진동공학회:학술대회논문집
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• 한국소음진동공학회 1996년도 춘계학술대회논문집; 부산수산대학교, 10 May 1996
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• pp.361-369
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• 1996

The accurate prediction of modal parameters of a rotating blade is an important requirement in the assessment of the dynamics of a helicopter rotor. Indeed, predictions of flight loads and stability are normally dependent on initially predicting the undamped mode shapes. A measuring technique, known as Strain Pattern Analysis (SPA), appears to be the most successful technique for measuring the mode shapes of rotating blades. This method was developed to be used on actual aircraft so no attempt was made to measure rotating mode shapes directly in order to validate the SPA method. This report summarizes results from experimental investigations which were carried out to validate the SPA method for the prediction of aerodynamically damped modes of a rotating blade. A series of modal tests were carried out on two rotor models in which the non-rotating, undamped and aerodynamically damped rotating modes were measured directly (strain and displacement patterns). It is shown that the SPA method to be very successful in itself but there are a number of limitations in validating this technique. To provide data which could be used to confidently validate theoretical prediction codes, existing limitations should be addressed.

• 한국소음진동공학회:학술대회논문집
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• 한국소음진동공학회 2008년도 추계학술대회논문집
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• pp.256-263
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• 2008

The assumed modes method is developed to derive a set of linear differential equations describing the motion of a flexible wind turbine blade and to propose an approach to investigate the forced responses result from various wind excitations. In this work, we have adopted Euler beam theory and considered that the root of the blade is clamped at the rigid hub. And the aerodynamic parameters and forces are determined based on Blade Element Momentum (BEM) theory and quasi-steady airfoil aerodynamics. Numerical calculations show that this method gives good results and it can be used fur modeling and the forced vibration analysis including the coupling effect of wind-turbine blades, as well as turbo-machinery blades, aircraft propellers or helicopter rotor blades which may be considered as straight non-uniform beams with built-in pre-twist.

• 한국소음진동공학회:학술대회논문집
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• 한국소음진동공학회 2007년도 춘계학술대회논문집
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• pp.85-92
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• 2007

This paper presents a design optimization of a new Advanced Active Blade Twist (AATR-II) blade incorporating single crystal Macro Fiber Composites (MFC) and conducts vibratory loads reduction analysis using an obtained optimal blade configuration. Due to the high actuation performance of the single crystal MFC, the AATR blade may reduce the helicopter vibration more efficiently even with a lower input-voltage as compared with the previous ATR blades. The design optimization provides the optimal cross-sectional configuration to maximize the tip twist actuation when a certain input-voltage is given. In order to maintain the properties of the original ATR blade, various constraints and bounds are considered for the design variables selected. After the design optimization is completed successfully, vibratory load reduction analysis of the optimized AATR-II blade in forward flight condition is conducted. The numerical result shows that the hub vibratory loads are reduced significantly although 20% input-voltage of the original ATR blade is used.

• 한국소음진동공학회논문집
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• 제16권9호
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• pp.926-936
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• 2006

In this study, structural vibration analyses of a smart unmanned aerial vehicle (UAV) have been conducted considering dynamic loads generated by rotating rotor and wakes. The present UAV (TR-S5-03) finite element model is constructed as a full three-dimensional configuration with different fuel conditions and tilting angles for helicopter, transition and airplane flight modes. Practical computational procedure for modal transient response analysis (MTRA) is established using general purpose finite element method (FEM) and computational fluid dynamics (CFD) technique. The dynamic loads generated by rotating blades in the transient and forward flight conditions are calculated by unsteady CFD technique with sliding mesh concept. As the results of present study, transient structural displacements and accelerations are presented in detail. In addition, vibration characteristics of structural parts and installed equipments are investigated for different fuel conditions and tilting angles.